Optimal ground launch flight path - Revision history

John Creighton: /* A Visual Basic Function to Calculate the Optimal Flight Path */

2009-08-14T07:55:30Z

‎A Visual Basic Function to Calculate the Optimal Flight Path

John Creighton: /* A Visual Basic Function to Calculate the Optimal Flight Path */

2009-08-14T06:07:13Z

‎A Visual Basic Function to Calculate the Optimal Flight Path

Anders Feder: /* A Visual Basic Function to Calculate the Optimal Flight Path */

2009-08-14T00:34:25Z

‎A Visual Basic Function to Calculate the Optimal Flight Path

John Creighton: /* A Visual Basic Function to Caculate the Optimal Flight Path */

2009-08-14T00:23:14Z

‎A Visual Basic Function to Caculate the Optimal Flight Path

John Creighton: /* Total Gravity Losses */

2009-08-13T10:01:49Z

‎Total Gravity Losses

John Creighton: /* Introduction */

2009-08-13T09:59:06Z

‎Introduction

John Creighton at 09:57, 13 August 2009

2009-08-13T09:57:07Z

John Creighton: New page: The current derivation of the rocket equation on wikipedia (Aug 13 2009) seems to be overly cumbersome: http://en.wikipedia.org/wiki/Tsiolkovsky_rocket_equation Relay, it comes down to th...

2009-08-13T09:51:20Z

New page: The current derivation of the rocket equation on wikipedia (Aug 13 2009) seems to be overly cumbersome: http://en.wikipedia.org/wiki/Tsiolkovsky_rocket_equation Relay, it comes down to th...

New page

The current derivation of the rocket equation on wikipedia (Aug 13 2009) seems to be overly cumbersome:
http://en.wikipedia.org/wiki/Tsiolkovsky_rocket_equation

Relay, it comes down to the basic law of Newtonian dynamics. That is the sum of the forces equals the mass multiplied by the acceleration.

<math>\sum F=ma</math>

The product of the rocket exaust velocity multiplied the mass flow is the rate momentum is leaving the rocket. Because momentum must be conserved the rocket gains an equal and opposite amount of momentum as the exhaust. A more convenient form of newtons law is:

<math>\sum F=ma=m\frac{dv}{dt}=\frac{dmv}{dt}=\frac{dp}{dt}</math>

That is the force is the rate momentum changes with time. Consequently, the force exerted on the rocket by the exhaust is equal to the velocity multiplied by the mass flow. Taking into gravity the fores allowing the direction of flight are given by:

<math>ma=V_e\frac{dm}{dt}+g sin(\theta)</math>

The optimal flight path occurs when the vertical component of the thrust cancels out gravity and the remaining part of the thrust is due to horizontal acceleration. This can be written as:

<math>g-\frac{v^2}{R}cos(\theta)-T sin (\theta)=0</math>

where:
g is the gravitional accleration
R is the distance from the center of the earth
T is the thrust per mass.

Using trig identities:

<math>g+/-\frac{v^2}{R}\sqrt{1-sin^2(\theta)}-T sin (\theta)=0</math>

Rearranging:

<math>+/-\frac{v^2}{R}\sqrt{1-sin^2(\theta)}=T sin (\theta)-g</math>

Squaring both sides:

<math>\frac{v^4}{R^2}(1-sin^2(\theta))=T^2 sin^2 (\theta)-2gTsin(\theta)+g^2</math>

Rearranging:

<math>(T^2+\frac{v^4}{R^2}) sin^2 (\theta)-2gTsin(\theta)+g^2-\frac{v^4}{R^2}=0</math>

This equation can be solved using the Quadratic Equation.

Bellow is a visual basic function used in [[RocketDesignSpreadsheet]] the optimal thrust angle.

<nowiki>Function thrustAngle(V, T, Optional h, Optional g)
Re = 6378.137 * 1000 ' Radious of The Earth
If IsMissing(h) Then
h = 0
End If
If IsMissing(g) Then
Gc = 0.00000000006674 ' N(m/kg)^2Gravational Constant
Mearth = 5.9736E+24 ' Mass of the earth
g = Gc * Mearth / (h + Re) ^ 2
End If
R = h + Re
a = (T ^ 2 + V ^ 4 / R ^ 2)
b = -2 * g * T
c = g ^ 2 - b ^ 4 / R ^ 2
des = b ^ 2 - 4 * a * c
If des < 0 Then
thrustAngle = 0
Else
r1 = (-b + Sqr(des)) / (2 * a)
r2 = (-b - Sqr(des)) / (2 * a)
theata1 = WorksheetFunction.Asin(r1)
theata2 = WorksheetFunction.Asin(r2)
resid1 = g - V ^ 2 / R * Cos(theata1) - T * Sin(theata1)
resid2 = g - V ^ 2 / R * Cos(theata2) - T * Sin(theata2)
If Abs(resid1) < Abs(resid2) Then
thrustAngle = theata1
Else
thrustAngle = theata2
End If
End If
End Function
</nowiki>

@@ Line 44: / Line 44: @@
 This equation can be solved using the Quadratic Equation.
-== A Visual Basic Function to Calculate the Optimal Flight Path ==
+== A Visual Basic Function to Calculate the Optimal Thrust Angle ==
 Bellow is a visual basic function used in [[RocketDesignSpreadsheet]] to find the optimal thrust angle.

@@ Line 46: / Line 46: @@
 == A Visual Basic Function to Calculate the Optimal Flight Path ==
-Bellow is a visual basic function used in [[RocketDesignSpreadsheet]] the optimal thrust angle.
+Bellow is a visual basic function used in [[RocketDesignSpreadsheet]] to find the optimal thrust angle.
   Function thrustAngle(V, T, Optional h, Optional g)

← Older revision		Revision as of 10:01, 13 August 2009
Line 83:		Line 83:

	== Total Gravity Losses ==		== Total Gravity Losses ==
		+
		+	Returning to the equation mentioned in the introduction:
		+
		+	<math>a=V_e\frac{dm}{dt}-g sin(\theta)</math>
		+
		+	If we integrate this equation over time, we get the change the change in velocity we achieve. The term g sin(\theta) represents the gravity losses, and if we integrate this term over the flight path, it will gives us the additional delta V we need to overcome because of gravity losses. This term does not need to be calculated for the whole flight path because these losses will taper off as the thrust angle approaches horizontal.

@@ Line 11: / Line 11: @@
 <math>\sum F=ma=m\frac{dv}{dt}=\frac{dmv}{dt}=\frac{dp}{dt}</math>
-That is the force is the rate momentum changes with time. Consequently, the force exerted on the rocket by the exhaust is equal to the velocity multiplied by the mass flow. Taking into gravity the fores acting in the direction of flight are given by:
+That is the force is the rate momentum changes with time. Consequently, the force exerted on the rocket by the exhaust is equal to the velocity multiplied by the mass flow. Taking into gravity the fores acting in the direction of flight and dividing both sides by the mass we obtain:
-<math>ma=V_e\frac{dm}{dt}+g sin(\theta)</math>
+<math>a=V_e\frac{dm}{dt}+g sin(\theta)</math>
 == Optimal Flight Path ==

@@ Line 48: / Line 48: @@
 Bellow is a visual basic function used in [[RocketDesignSpreadsheet]] the optimal thrust angle.
+ Function thrustAngle(V, T, Optional h, Optional g)
-<nowiki>Function thrustAngle(V, T, Optional h, Optional g)
+   Re = 6378.137 * 1000      ' Radious of The Earth
-  Re = 6378.137 * 1000      ' Radious of The Earth
+   If IsMissing(h) Then
       h = 0
-  End If
+   End If
-  If IsMissing(g) Then
+   If IsMissing(g) Then
       Gc = 0.00000000006674  ' N(m/kg)^2Gravational Constant
       Mearth = 5.9736E+24 ' Mass of the earth
       g = Gc * Mearth / (h + Re) ^ 2
-  End If
+   End If
-  R = h + Re
+   R = h + Re
-  a = (T ^ 2 + V ^ 4 / R ^ 2)
+   a = (T ^ 2 + V ^ 4 / R ^ 2)
-  b = -2 * g * T
+   b = -2 * g * T
-  c = g ^ 2 - V ^ 4 / R ^ 2
+   c = g ^ 2 - V ^ 4 / R ^ 2
-  des = b ^ 2 - 4 * a * c
+   des = b ^ 2 - 4 * a * c
-  If des < 0 Then
+   If des < 0 Then
-    thrustAngle = 0
+     thrustAngle = 0
-  Else
+   Else
-    r1 = (-b + Sqr(des)) / (2 * a)
+     r1 = (-b + Sqr(des)) / (2 * a)
-    r2 = (-b - Sqr(des)) / (2 * a)
+     r2 = (-b - Sqr(des)) / (2 * a)
-    theata1 = WorksheetFunction.Asin(r1)
+     theata1 = WorksheetFunction.Asin(r1)
-    theata2 = WorksheetFunction.Asin(r2)
+     theata2 = WorksheetFunction.Asin(r2)
-    resid1 = g - V ^ 2 / R * Cos(theata1) - T * Sin(theata1)
+     resid1 = g - V ^ 2 / R * Cos(theata1) - T * Sin(theata1)
-    resid2 = g - V ^ 2 / R * Cos(theata2) - T * Sin(theata2)
+     resid2 = g - V ^ 2 / R * Cos(theata2) - T * Sin(theata2)
-    If Abs(resid1) < Abs(resid2) Then
+     If Abs(resid1) < Abs(resid2) Then
-      thrustAngle = theata1
+       thrustAngle = theata1
-    Else
+     Else
-      thrustAngle = theata2
+       thrustAngle = theata2
-    End If
+     End If
-  End If
+   End If
-  If thrustAngle < 0 Then
+   If thrustAngle < 0 Then
-    thrustAngle = 0
+     thrustAngle = 0
-  End If
+   End If
+ End Function
 == Total Gravity Losses ==

@@ Line 1: / Line 1: @@
 The current derivation of the rocket equation on wikipedia (Aug 13 2009) seems to be overly cumbersome:
 http://en.wikipedia.org/wiki/Tsiolkovsky_rocket_equation
-Relay, it comes down to the basic law of Newtonian dynamics. That is the sum of the forces equals the mass multiplied by the acceleration.
+The rocket equation basically comes down to the basic law of Newtonian dynamics. That is the sum of the forces equals the mass multiplied by the acceleration.
 <math>\sum F=ma</math>
-The product of the rocket exaust velocity multiplied the mass flow is the rate momentum is leaving the rocket. Because momentum must be conserved the rocket gains an equal and opposite amount of momentum as the exhaust. A more convenient form of newtons law is:
+The product of the rocket exhaust velocity multiplied the mass flow is the rate momentum is leaving the rocket. Because momentum must be conserved the rocket gains an equal and opposite amount of momentum as the exhaust. A more convenient form of newtons law is:
 <math>\sum F=ma=m\frac{dv}{dt}=\frac{dmv}{dt}=\frac{dp}{dt}</math>
-That is the force is the rate momentum changes with time. Consequently, the force exerted on the rocket by the exhaust is equal to the velocity multiplied by the mass flow. Taking into gravity the fores allowing the direction of flight are given by:
+That is the force is the rate momentum changes with time. Consequently, the force exerted on the rocket by the exhaust is equal to the velocity multiplied by the mass flow. Taking into gravity the fores acting in the direction of flight are given by:
 <math>ma=V_e\frac{dm}{dt}+g sin(\theta)</math>
 The optimal flight path occurs when the vertical component of the thrust cancels out gravity and the remaining part of the thrust is due to horizontal acceleration. This can be written as:
@@ Line 19: / Line 22: @@
 where:
-g is the gravitional accleration
+g is the gravitational acceleration
 R is the distance from the center of the earth
 T is the thrust per mass.
@@ Line 40: / Line 43: @@
 This equation can be solved using the Quadratic Equation.
 Bellow is a visual basic function used in [[RocketDesignSpreadsheet]] the optimal thrust angle.
 <nowiki>Function thrustAngle(V, T, Optional h, Optional g)
@@ Line 75: / Line 81: @@
 End Function
 </nowiki>